FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il) Reynolds number: 500,000 Max Cl/Cd: 105.36 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s196-il-500000.txt Download as CSV file: xf-fx66s196-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.3303 0.10358 0.10071 -0.0945 0.8487 0.0172
-15.250 -0.3727 0.09016 0.08719 -0.1014 0.8415 0.0165
-15.000 -0.4739 0.06799 0.06461 -0.1147 0.8427 0.0151
-14.750 -0.4809 0.06416 0.06057 -0.1168 0.8199 0.0153
-14.500 -0.5024 0.05881 0.05497 -0.1192 0.8046 0.0155
-14.250 -0.5402 0.05199 0.04779 -0.1212 0.7927 0.0152
-14.000 -0.5322 0.05102 0.04675 -0.1216 0.7786 0.0159
-13.750 -0.5538 0.04658 0.04201 -0.1221 0.7685 0.0157
-13.500 -0.5597 0.04409 0.03934 -0.1222 0.7586 0.0160
-13.250 -0.5717 0.04077 0.03576 -0.1218 0.7504 0.0159
-13.000 -0.5731 0.03890 0.03371 -0.1214 0.7419 0.0164
-12.750 -0.5763 0.03664 0.03122 -0.1207 0.7347 0.0166
-12.500 -0.5750 0.03467 0.02906 -0.1199 0.7275 0.0166
-12.250 -0.5726 0.03313 0.02730 -0.1190 0.7212 0.0169
-12.000 -0.5680 0.03163 0.02563 -0.1180 0.7147 0.0171
-11.750 -0.5604 0.02977 0.02355 -0.1169 0.7092 0.0174
-11.500 -0.5467 0.02834 0.02207 -0.1161 0.7039 0.0180
-11.250 -0.5333 0.02722 0.02087 -0.1152 0.6983 0.0183
-11.000 -0.5208 0.02634 0.01990 -0.1143 0.6933 0.0187
-10.750 -0.5087 0.02563 0.01914 -0.1135 0.6882 0.0193
-10.500 -0.4942 0.02473 0.01815 -0.1126 0.6832 0.0199
-10.250 -0.4787 0.02385 0.01717 -0.1116 0.6788 0.0202
-10.000 -0.4639 0.02312 0.01632 -0.1106 0.6747 0.0208
-9.750 -0.4484 0.02233 0.01547 -0.1096 0.6705 0.0212
-9.500 -0.4333 0.02164 0.01469 -0.1084 0.6665 0.0215
-9.250 -0.4216 0.02054 0.01352 -0.1068 0.6630 0.0221
-9.000 -0.4140 0.01964 0.01258 -0.1047 0.6596 0.0229
-8.750 -0.4044 0.01910 0.01203 -0.1027 0.6561 0.0237
-8.500 -0.3905 0.01852 0.01140 -0.1013 0.6527 0.0243
-8.250 -0.3742 0.01799 0.01081 -0.1001 0.6495 0.0254
-8.000 -0.3571 0.01749 0.01021 -0.0990 0.6465 0.0262
-7.750 -0.3376 0.01707 0.00972 -0.0982 0.6436 0.0270
-7.500 -0.3251 0.01613 0.00876 -0.0966 0.6407 0.0288
-7.250 -0.3053 0.01562 0.00823 -0.0959 0.6377 0.0308
-7.000 -0.2835 0.01521 0.00775 -0.0954 0.6348 0.0332
-6.750 -0.2633 0.01464 0.00717 -0.0947 0.6321 0.0378
-6.500 -0.2405 0.01427 0.00674 -0.0944 0.6293 0.0444
-6.250 -0.2171 0.01384 0.00633 -0.0941 0.6270 0.0540
-6.000 -0.1942 0.01335 0.00593 -0.0938 0.6243 0.0700
-5.750 -0.1708 0.01288 0.00556 -0.0936 0.6216 0.0968
-5.500 -0.1480 0.01230 0.00517 -0.0935 0.6192 0.1420
-5.250 -0.1259 0.01160 0.00474 -0.0933 0.6170 0.2171
-5.000 -0.1057 0.01066 0.00423 -0.0931 0.6147 0.3331
-4.750 -0.0850 0.01001 0.00419 -0.0925 0.6127 0.4707
-4.500 -0.0559 0.01013 0.00419 -0.0928 0.6107 0.5118
-4.250 -0.0275 0.01024 0.00426 -0.0930 0.6087 0.5274
-4.000 0.0010 0.01036 0.00437 -0.0932 0.6067 0.5391
-3.750 0.0297 0.01050 0.00447 -0.0934 0.6048 0.5490
-3.500 0.0586 0.01064 0.00453 -0.0936 0.6031 0.5566
-3.250 0.0874 0.01071 0.00452 -0.0940 0.6014 0.5614
-3.000 0.1164 0.01090 0.00468 -0.0942 0.5998 0.5685
-2.750 0.1454 0.01113 0.00479 -0.0946 0.5981 0.5750
-2.500 0.1738 0.01115 0.00486 -0.0948 0.5967 0.5796
-2.250 0.2024 0.01126 0.00497 -0.0950 0.5951 0.5847
-2.000 0.2311 0.01145 0.00508 -0.0953 0.5935 0.5912
-1.750 0.2594 0.01147 0.00517 -0.0954 0.5919 0.5964
-1.500 0.2881 0.01156 0.00523 -0.0957 0.5904 0.6002
-1.250 0.3170 0.01161 0.00523 -0.0961 0.5889 0.6030
-1.000 0.3459 0.01164 0.00520 -0.0966 0.5874 0.6049
-0.750 0.3749 0.01168 0.00518 -0.0971 0.5859 0.6064
-0.500 0.4039 0.01173 0.00517 -0.0976 0.5844 0.6079
-0.250 0.4329 0.01180 0.00521 -0.0981 0.5829 0.6092
0.000 0.4611 0.01179 0.00522 -0.0984 0.5817 0.6101
0.250 0.4893 0.01181 0.00524 -0.0988 0.5805 0.6109
0.500 0.5176 0.01183 0.00527 -0.0992 0.5791 0.6116
0.750 0.5460 0.01186 0.00531 -0.0995 0.5777 0.6122
1.000 0.5744 0.01190 0.00535 -0.0999 0.5763 0.6129
1.250 0.6029 0.01195 0.00539 -0.1004 0.5749 0.6138
1.500 0.6315 0.01200 0.00544 -0.1008 0.5735 0.6148
1.750 0.6602 0.01206 0.00550 -0.1012 0.5722 0.6157
2.000 0.6890 0.01213 0.00555 -0.1017 0.5710 0.6166
2.250 0.7179 0.01222 0.00563 -0.1022 0.5698 0.6174
2.500 0.7469 0.01237 0.00576 -0.1028 0.5685 0.6184
2.750 0.7753 0.01256 0.00596 -0.1033 0.5670 0.6194
3.000 0.8023 0.01261 0.00606 -0.1034 0.5657 0.6202
3.250 0.8294 0.01269 0.00618 -0.1036 0.5643 0.6210
3.500 0.8566 0.01277 0.00630 -0.1038 0.5627 0.6217
3.750 0.8839 0.01285 0.00641 -0.1041 0.5610 0.6225
4.000 0.9115 0.01293 0.00652 -0.1043 0.5592 0.6233
4.250 0.9392 0.01298 0.00662 -0.1046 0.5578 0.6246
4.500 0.9671 0.01307 0.00676 -0.1050 0.5565 0.6261
4.750 0.9954 0.01318 0.00690 -0.1054 0.5552 0.6275
5.000 1.0241 0.01329 0.00703 -0.1059 0.5537 0.6288
5.250 1.0532 0.01352 0.00727 -0.1065 0.5519 0.6301
5.500 1.0786 0.01363 0.00748 -0.1064 0.5503 0.6317
5.750 1.1036 0.01374 0.00768 -0.1063 0.5485 0.6332
6.000 1.1290 0.01385 0.00787 -0.1062 0.5465 0.6350
6.250 1.1550 0.01391 0.00800 -0.1061 0.5443 0.6368
6.500 1.1821 0.01394 0.00806 -0.1063 0.5419 0.6387
6.750 1.2103 0.01391 0.00807 -0.1067 0.5395 0.6408
7.000 1.2404 0.01396 0.00812 -0.1074 0.5363 0.6432
7.250 1.2599 0.01389 0.00821 -0.1061 0.5325 0.6457
7.500 1.2835 0.01380 0.00820 -0.1055 0.5282 0.6487
7.750 1.3104 0.01361 0.00800 -0.1054 0.5236 0.6521
8.000 1.3322 0.01360 0.00807 -0.1046 0.5186 0.6555
8.250 1.3508 0.01345 0.00802 -0.1030 0.5119 0.6594
8.500 1.3753 0.01339 0.00795 -0.1026 0.5059 0.6638
8.750 1.3871 0.01337 0.00811 -0.0998 0.4984 0.6689
9.000 1.4050 0.01337 0.00814 -0.0982 0.4916 0.6742
9.250 1.4160 0.01344 0.00837 -0.0954 0.4836 0.6805
9.750 1.4322 0.01377 0.00885 -0.0887 0.4625 0.6960
10.000 1.4387 0.01417 0.00930 -0.0855 0.4489 0.7058
10.250 1.4395 0.01486 0.00999 -0.0817 0.4314 0.7176
10.500 1.4339 0.01602 0.01115 -0.0776 0.4024 0.7315
10.750 1.4165 0.01814 0.01319 -0.0728 0.3712 0.7495
11.000 1.3988 0.02110 0.01610 -0.0694 0.3361 0.7765
11.250 1.3798 0.02511 0.02010 -0.0677 0.3014 0.8182
11.500 1.3754 0.03139 0.02641 -0.0729 0.2490 0.9271
11.750 1.3629 0.03585 0.03075 -0.0727 0.2169 1.0000
12.000 1.3454 0.03995 0.03472 -0.0710 0.1925 1.0000
12.250 1.3307 0.04389 0.03852 -0.0696 0.1643 1.0000
12.500 1.3202 0.04751 0.04202 -0.0684 0.1412 1.0000
12.750 1.3072 0.05144 0.04578 -0.0672 0.1139 1.0000
13.000 1.2993 0.05490 0.04912 -0.0663 0.0916 1.0000
13.250 1.2915 0.05840 0.05247 -0.0654 0.0708 1.0000
13.500 1.2881 0.06156 0.05555 -0.0648 0.0539 1.0000
14.000 1.2819 0.06787 0.06172 -0.0636 0.0310 1.0000
14.250 1.2818 0.07078 0.06459 -0.0632 0.0249 1.0000
14.500 1.2830 0.07362 0.06744 -0.0629 0.0219 1.0000
14.750 1.2831 0.07658 0.07045 -0.0626 0.0193 1.0000
15.000 1.2866 0.07918 0.07311 -0.0624 0.0179 1.0000
15.250 1.2852 0.08241 0.07637 -0.0622 0.0165 1.0000
15.500 1.2878 0.08520 0.07922 -0.0621 0.0156 1.0000
15.750 1.2915 0.08789 0.08197 -0.0622 0.0144 1.0000
16.000 1.2939 0.09073 0.08488 -0.0622 0.0142 1.0000
16.250 1.2955 0.09367 0.08785 -0.0622 0.0132 1.0000
16.500 1.2903 0.09748 0.09171 -0.0623 0.0126 1.0000
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Polar data table (+)
Polar graphs
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